[Federal Register Volume 79, Number 39 (Thursday, February 27, 2014)]
[Proposed Rules]
[Pages 11016-11019]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-04259]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0061; Directorate Identifier 2013-NM-029-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede airworthiness directive (AD) 2007-06-
12, that applies to certain Airbus Model A330-200 and A330-300
airplanes. AD 2007-06-12 requires, for certain airplanes, reinforcement
of the structure of the center fuselage by installing external
stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin
between left-hand (LH) and right-hand (RH) stringer (STR) 13, and
related investigative and corrective actions. Since we issued AD 2007-
06-12, we have determined that the compliance times must be reduced in
order to address the unsafe condition. This proposed AD would reduce
the compliance times for reinforcing the structure of the center
fuselage at FR 53.3. We are proposing this AD to prevent fatigue
cracking of the fuselage, which could result in reduced structural
integrity of the fuselage.
DATES: We must receive comments on this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0061; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1138;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0061;
Directorate Identifier 2013-NM-029-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 7, 2007, we issued AD 2007-06-12, Amendment 39-14993 (72
FR 12555, March 16, 2007) (``AD 2007-06-12''). AD 2007-06-12 requires
actions intended to address an unsafe condition on the products listed
above.
Since we issued AD 2007-06-12, Amendment 39-14993 (72 FR 12555,
March 16, 2007), we have determined that the compliance times must be
reduced in order to address the unsafe condition. We have also added
the
[[Page 11017]]
compliance time for short- and long-range airplane utilization based on
the new fatigue and damage tolerance evaluation. The European Aviation
Safety Agency (EASA), which is the Technical Agent for the Member
States of the European Community, has issued EASA Airworthiness
Directive 2013-0016, dated January 16, 2013 (referred to after this as
the Mandatory Continuing Airworthiness Information, or ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
During the fatigue tests (EF2) of the Airbus A330 test fuselage,
initiation and development of cracks were evidenced at the
circumferential joint of frame 53.3.
This condition, if not corrected, could lead to a reduction in
the structural integrity of the fuselage.
EASA issued AD 2006-0266 [(http://ad.easa.europa.eu/blob/easa_ad_2006_0266_Superseded.pdf/AD_2006-0266_1), which corresponds
to FAA AD 2007-06-12, Amendment 39-14993 (72 FR 12555, March 16,
2007)], which took over the requirements of Direction
G[eacute]n[eacute]rale de L'aviation Civile [DGAC] France AD F-2003-
415 for A330-300 pre-mod 41652S11819, and required reinforcement of
the circumferential joint of frame 53.3 by application of Airbus
Service Bulletin (SB) A330-53-3143 on A330-300 post modification
41652S11819 and pre-mod 49202, and all A330-200 pre-mod 49202 in
order to improve the fatigue life.
Since that [EASA] AD was issued, in the frame of a new fatigue
and damage tolerance evaluation taking into account the aeroplane
utilisation, the thresholds for the reinforcement were reassessed
and the conclusion is that some thresholds must be reduced.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2006-0266, which is superseded, and requires
reinforcement of structure of the centre fuselage at the upper
circumferential joint of frame 53.3 within the new thresholds.
The initial compliance times range between 15,700 total flight
cycles or 94,600 total flight hours, whichever occurs first; and 25,600
total flight cycles or 77,000 total flight hours, whichever occurs
first; depending on airplane configuration. You may examine the MCAI in
the AD docket on the Internet at http://www.regulations.gov by
searching for and locating it in Docket No. FAA-2014-0061.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A330-53-3127 Revision
02, including Appendix 01, dated December 7, 2011, and Mandatory
Service Bulletin A330-53-3143 Revision 05, including Appendix 01, dated
May 29, 2012. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Repair Approvals
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD would require that the repair approval specifically refer to the FAA
AD. This change is intended to clarify the method of compliance and to
provide operators with better visibility of repairs that are
specifically developed and approved to correct the unsafe condition. In
addition, we use the phrase ``its delegated agent, or the DAH with
State of Design Authority design organization approval, as applicable''
in this proposed AD to refer to a DAH authorized to approve certain
required repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 9 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD.
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Installation................... Up to 327 $17,850 Up to $45,645..... Up to $410,805.
work[dash]hour x $85
per hour = $27,795.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This
[[Page 11018]]
proposed AD would not have a substantial direct effect on the States,
on the relationship between the national Government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2007-06-12, Amendment 39-14993 (72 FR 12555, March 16, 2007), and
adding the following new AD:
Airbus: Docket No. FAA-2014-0061; Directorate Identifier 2013-NM-
029-AD.
(a) Comments Due Date
We must receive comments by April 14, 2014.
(b) Affected ADs
This AD supersedes AD 2007-06-12, Amendment 39-14993 (72 FR
12555, March 16, 2007).
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, and
-243 airplanes; and A330-301, -321, -322, -323, -341, -342, and -343
airplanes, certificated in any category, except those on which
Airbus modification 49202 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a new fatigue and damage tolerance
evaluation that concluded the compliance time for an existing
reinforcement of the fuselage has to be reduced. We are issuing this
AD to prevent fatigue cracking of the fuselage, which could result
in reduced structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Installation for Model A330-300 Series Airplanes
For Airbus Model A330-301, A330-321, A330-322, A330-323, A330-
341, A330-342, and A330-343 airplanes, except those on which Airbus
modification 41652S11819 has been incorporated in production: At the
time specified in paragraph (g)(1) or (g)(2) of this AD, whichever
occurs later, install butt straps at FR53.3 on the fuselage skin
between left-hand (LH) and right-hand (RH) stringer (STR) 13, and do
all related investigative and corrective actions before further
flight. Except as provided by paragraph (h) of this AD, do all
actions in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-53-3127, Revision 02, including
Appendix 01, dated December 7, 2011.
(1) At the applicable time specified in paragraph (g)(1)(i) or
(g)(1)(ii) of this AD.
(i) Airplanes with a short-range mission as specified in Airbus
Mandatory Service Bulletin A330-53-3127, Revision 02, dated December
7, 2011: Within 15,300 flight cycles or 46,100 flight hours,
whichever occurs first, after the first flight of the airplane.
(ii) Airplanes with a long-range mission as specified in Airbus
Mandatory Service Bulletin A330-53-3127, Revision 02, dated December
7, 2011: Within 13,200 flight cycles or 79,300 flight hours,
whichever occurs first after the first flight of the airplane.
(2) Within 24 months after the effective date of this AD, but
not to exceed 14,700 total flight cycles or 51,400 total flight
hours, whichever occurs earlier.
(h) Corrective Actions
For Airbus Model A330-301, -321, -322, -323, -341, -342, and -
343 airplanes, except those on which Airbus Modification 41652S11819
has been incorporated in production: If any crack is detected during
the related investigative actions (rototest) required by paragraph
(g) of this AD, before further flight, repair using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA (or its delegated agent, or
by the Design Approval Holder (DAH) with EASA design organization
approval). For a repair method to be approved, the repair approval
must specifically refer to this AD.
(i) Installation for Model A330-200 and -300 Series Airplanes
For airplanes specified in paragraph (c) of this AD on which
Airbus modification 41652S11819 has been embodied in production: At
the time specified in paragraph (i)(1) or (i)(2) of this AD,
whichever occurs later, install butt straps at FR53.3 on the
fuselage skin between LH and RH STR13; and do all related
investigative and other specified actions before further flight, as
applicable. Do all actions in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-53-3143,
Revision 05, dated May 29, 2012, including Appendix 1; except, if
any crack is detected during a related investigative action
(rototest), before further flight, repair the crack using a method
approved by the Manager, International Branch, ANM 116, Transport
Airplane Directorate, FAA; or the EASA (or its delegated agent, or
by the Design Approval Holder (DAH) with EASA design organization
approval). For a repair method to be approved, the repair approval
must specifically refer to this AD.
(1) At the applicable times specified in the ``threshold''
column of the table in 1.E. ``Compliance'' of Airbus Mandatory
Service Bulletin A330-53-3143, Revision 05, dated May 29, 2012.
Where paragraph 1.E. ``Compliance'' of Airbus Mandatory Service
Bulletin A330 53-3143, Revision 05, dated May 29, 2012, specifies a
time in the ``threshold'' column, this AD requires compliance within
the corresponding times after the first flight of the airplane.
(2) Within 24 months after the effective date of this AD, but
not to exceed 17,600 total flight cycles or 61,600 total flight
hours, whichever occurs earlier.
(j) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (g) of this AD if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A330-53-
3127, Revision 01, including Appendix 01, dated November 21, 2003
(which is not incorporated by reference in this AD).
(2) This paragraph provides credit for actions required by
paragraph (i) of this AD if those actions were performed before the
effective date of this AD using any service information specified in
paragraphs (j)(2)(i) through (j)(2)(v) of this AD; this service
information is not incorporated by reference in this AD.
(i) Airbus Mandatory Service Bulletin A330-53-3143, including
Appendix 01, dated December 24, 2004.
(ii) Airbus Mandatory Service Bulletin A330-53-3143, Revision
01, including Appendix 01, dated June 29, 2006.
(iii) Airbus Mandatory Service Bulletin A330-53-3143, Revision
02, including Appendix 01, dated August 31, 2010.
(iv) Airbus Mandatory Service Bulletin A330-53-3143, Revision
03, including Appendix 01, dated March 3, 2011.
(v) Airbus Mandatory Service Bulletin A330-53-3143, Revision 04,
including Appendix 01, dated December 6, 2011.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International
[[Page 11019]]
Branch, ANM-116, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the International Branch, send it
to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch,
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD. AMOCs approved previously for AD 2007-06-12, Amendment 39-14993
(72 FR 12555, March 16, 2007), are approved as AMOCs for the
corresponding provisions of paragraph (i) of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval). You are required to ensure the
product is airworthy before it is returned to service.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0016, dated January 16,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0061.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email [email protected];
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-04259 Filed 2-26-14; 8:45 am]
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